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EFFECTIVITY 30-21-00 Page 3
Aug 31/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 43
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THIS PAGE INTENTIONALLY LEFT BLANK
TMUIC3E03 LEVEL 2
EFFECTIVITY 30-21-00 Page 4
Aug 31/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 44
ALL
30 - ICE AND RAIN PROTECTION
30-31-00 PROBES ICE PROTECTION SYSTEM
PRESENTATION
CONTENTS:
Function
Control
Probe Heat Computer
Caution
Self Examination
TMUICE501 LEVEL 1
EFFECTIVITY 30-31-00 Page 1
Aug 31/97
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 45
ALL
PROBES ICE PROTECTION SYSTEM PRESENTATION
FUNCTION
The static ports, Angle Of Attack (AOA), pitot and
Total Air Temperature (TAT) probes are electrically
heated to prevent ice formation.
The captain, first officer and standby systems are
independent.
Each one consists of a Probe Heat Computer (PHC) which
controls probe and static port heating.
As there are only 2 TAT (CAPT and F/O) probes, PHC 3
is not linked to a TAT probe.
CONTROL
Probes and static ports heating comes on automatically
when at least one engine is running.
It can also be activated by the "PROBE/WINDOW HEAT"
pushbutton.
On ground, pitot heating is reduced and TAT heating
is cut off.
LGCIU (Landing Gear Control and Interface Unit).
PROBE HEAT COMPUTER
Heating monitoring and fault indication are
provided by the related Probe Heat Computer.
A probe or a sensor heating failure is sent to the
ECAM via Air Data Inertial Reference Unit (ADIRU)
and Flight Warning Computers (FWCs).
The PHC also transmits fault messages to the
Centralized Fault Display Interface Unit (CFDIU).
CAUTION
Pulling the Probe Heat Computer (PHC) or Engine
Interface Unit (EIU) power supply circuit breakers
causes unwanted heating of the probes and static ports.
TMUICE501-T01 LEVEL 1
EFFECTIVITY 30-31-00 Page 2
Aug 31/97
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 46
ALL
PROBES ICE PROTECTION SYSTEM PRESENTATION
TMUICE501-P01 LEVEL 1
EFFECTIVITY 30-31-00 Page 3
Aug 31/97
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 47
ALL
SELF EXAMINATION
When is the TAT probe heated ?
A - In flight, not on ground.
B - On ground, not in flight.
C - In icing conditions only.
When is the pitot probe heated ?
A - In flight, not on ground.
B - In icing conditions only.
C - Normal heating in flight, low heating on
ground.
TMUICE501 LEVEL 1
EFFECTIVITY 30-31-00 Page 4
Aug 31/97
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 48
ALL
30 - ICE AND RAIN PROTECTION
30-31-00 PROBES ICE PROTECTION SYSTEM
DESCRIPTION AND OPERATION
CONTENTS:
General
Control
Landing Gear Control and Interface Unit (LGCIU)
Engine Relays
Power Supply
Air Data Inertial Reference Unit (ADIRU)
Centralized Fault Display Interface Unit (CFDIU)
TMUICEY01 LEVEL 3
EFFECTIVITY 30-31-00 Page 1
Sep 30/98
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 49
ALL
PROBES ICE PROTECTION SYSTEM DESCRIPTION AND OPERATION
GENERAL
Typical probe heat schematic (see following page) is
shown : aircraft on ground and electrically supplied
and system "off".
Remind that standby probe heat system has no TAT
heating.
CONTROL
Probes and static ports heating comes on automatically
when at least one engine is running.
It can also be activated by the "PROBE/WINDOW HEAT"
pushbutton.
On ground, pitot heating is reduced and TAT heating
is cut off.
LANDING GEAR CONTROL AND INTERFACE UNIT (LGCIU)
When one of the three control conditions is met, the
flight condition enables heating of the TAT sensor and
full wave heating of the pitot probe.
ENGINE RELAYS
OIL LOW PRESSURE AND GROUND relays are energized by
　
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